[go: up one dir, main page]

EP2064025B1 - Procédé de réparation - Google Patents

Procédé de réparation Download PDF

Info

Publication number
EP2064025B1
EP2064025B1 EP07817519.7A EP07817519A EP2064025B1 EP 2064025 B1 EP2064025 B1 EP 2064025B1 EP 07817519 A EP07817519 A EP 07817519A EP 2064025 B1 EP2064025 B1 EP 2064025B1
Authority
EP
European Patent Office
Prior art keywords
blade
repaired
rotor blade
metal powder
design data
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Not-in-force
Application number
EP07817519.7A
Other languages
German (de)
English (en)
Other versions
EP2064025A1 (fr
Inventor
Anja Lange
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP2064025A1 publication Critical patent/EP2064025A1/fr
Application granted granted Critical
Publication of EP2064025B1 publication Critical patent/EP2064025B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P6/00—Restoring or reconditioning objects
    • B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
    • B23P6/007—Repairing turbine components, e.g. moving or stationary blades, rotors using only additive methods, e.g. build-up welding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B22F10/20—Direct sintering or melting
    • B22F10/28—Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B22F10/80—Data acquisition or data processing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P6/00—Restoring or reconditioning objects
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/005—Repairing methods or devices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/80—Repairing, retrofitting or upgrading methods
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P10/00—Technologies related to metal processing
    • Y02P10/25—Process efficiency
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49318—Repairing or disassembling

Definitions

  • the invention relates to a repair method for blades of a gas turbine.
  • the rotor blades of gas turbines are subject to high mechanical and thermal stresses during operation, which can lead to cracking, as well as additional stresses due to wear.
  • the above stresses on the blades may necessitate repairing them after damage by renewing a damaged portion of the blade, particularly a blade tip thereof, from the blade and renewing it after removal.
  • a method of repairing a stator of a gas turbine in which a damaged portion is cut out of the nozzle to be repaired and a spare part for the cut-out portion is manufactured by means of a rapid manufacturing process.
  • the spare part produced by the rapid manufacturing process is integrated into the guide vane to be repaired by welding or soldering.
  • Another method for repairing gas turbine blades is from the DE 43 27 189 C2 It is known in which a damaged portion is separated from an airfoil of the gas turbine blade to be repaired and in which subsequently a repair plate is welded to the remaining airfoil stump of the gas turbine blade. Subsequently, the repair plate is processed on the desired airfoil profile.
  • a method of repairing a gas turbine blade comprising the steps of: a) providing a blade to be repaired; b) removing at least one damaged portion of a damaged blade tip from the blade to be repaired to form a separation surface; c) successively building up the or each removed portion or blade tip on the blade separation surface by a rapid manufacturing method using three-dimensional CAD design data of the blade, wherein as a rapid manufacturing method a two-stage process is used in which in each first step uniform powder bed is provided from a metal powder which is formed of the same alloy base material as the blade to be repaired and in a second step is selectively welded based on the three-dimensional CAD design data metal powder of the powder bed, repeated.
  • WO 2006/024844 A2 For example, a method of fitting a workpiece to geometric design data using a coordinate positioning apparatus is known. In the described method, a workpiece to be produced is measured between two production steps and the actual contour obtained is compared with the desired contour. A "fitting algorithm" calculates an adjustment of the workpiece with the axes of the production machine or an adjustment of the control commands for subsequent processing steps.
  • the present invention based on the problem to provide a novel repair method for blades of a gas turbine.
  • the present invention provides a gas turbine blade repairing method by which high quality repair is possible.
  • the repair method according to the invention is suitable for a multiplicity of damage cases on moving blades.
  • the repair method according to the invention makes do without expensive model and mold construction and thus permits relatively inexpensive repair of rotor blades, even on integrally bladed rotors such as blisks and blings.
  • the separation surface is measured, wherein if an actual contour of the separation surface determined thereby is more than a defined amount of a target contour determined by the CAD design data of the blade Separates separation surface, the CAD design data are adapted to the actual contour, whereby a transition profile between the actual contour and the target contour is determined.
  • the present invention relates to a method for repairing blades of a gas turbine.
  • Gas turbine blades may be so severely damaged during operation, eg due to oxidation, corrosion or erosion in the area of a blade tip, that the damaged blade tip must be replaced completely or partially.
  • the damaged blade to be repaired is first provided, and then the damaged blade tip or at least a damaged portion thereof is removed from the blade to be repaired to form a separation surface. It also means sections that extend from the blade tip to the entry or exit edge of the blade.
  • the position of the parting line or separating line for separating the section or the damaged blade tip from the blade of the blade is made dependent on the one hand by strength requirements, on the other hand, in the region of the separating surface, the blade must be free of coatings and radial cracks.
  • a two-step process is repeated.
  • a uniform powder bed of a metal powder is provided, wherein in a second step, the metal powder of the powder bed is selectively welded based on the three-dimensional CAD design data. Repetitive execution of this two-stage process, the new blade tip is built successively on the interface.
  • a metal powder is provided whose chemical composition is ideally of chemical composition corresponds to the blade to be repaired. At least, however, a metal powder is provided which is formed of the same alloy base material as the blade to be repaired. For example, if the blade to be repaired is made of a nickel-base alloy, a metal powder of a nickel-base alloy is used to provide the uniform powder bed.
  • a powder bed is provided with a maximum thickness of 200 microns, wherein the average grain size of the metal powder is preferably between 10 .mu.m and 150 .mu.m.
  • the uniform application of the powder bed can be done for example by means of a scraper.
  • metal powder is selectively welded onto the parting surface by means of laser beam welding or electron beam welding.
  • the blade freed from the damaged portion or the damaged blade tip is positioned in a process chamber of a rapid manufacturing plant for carrying out the rapid manufacturing process. If several blades are to be repaired simultaneously in a rapid manufacturing plant with the aid of the method according to the invention, then the separating surfaces of the different blades must be aligned exactly in one plane.
  • the process space of the rapid manufacturing plant is preferably filled with the metal powder up to the separating surface of the blade to be repaired.
  • the process space of the rapid manufacturing plant is either evacuated or filled with an inert protective gas during the welding of the powder on the parting surface of the blade to be repaired, oxidation is prevented.
  • the blades are preheated to weld the metal powder.
  • the new blade tip may be built with an excess of the outer contour of the blade to be repaired. In this case, reworking the new blade tip is mandatory.
  • the forming separating surface is measured and in this case an actual contour of the separating surface is determined.
  • a desired contour for the separating surface can be derived from the CAD design data.
  • the measured actual contour deviates from the calculated target contour by more than a defined amount
  • Contour of the separating surface is determined. This makes it possible to determine geometry differences between the actual contour and the desired contour of the parting surface, e.g. can be caused by wear or by production tolerances, compensate.
  • the welding parameters for welding the metal powder in the rapid manufacturing process are matched to the blade to be repaired as well as the material thereof and the metal powder.
  • the welding parameters both a polycrystalline and a monocrystalline and a directed he-stared building a new blade tip on the separation surface of the blade done.
  • a blade repaired by the repair method of the present invention may optionally be subsequently coated, e.g. in the region of a suction side and pressure side of the blade of the blade.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Manufacturing & Machinery (AREA)
  • Materials Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Laser Beam Processing (AREA)
  • Powder Metallurgy (AREA)

Claims (6)

  1. Procédé de réparation d'aubes de rotor d'une turbine à gaz, comprenant au moins les étapes suivantes dans l'ordre d'énumération :
    a) fourniture d'une aube de rotor à réparer ;
    b) extraction d'au moins une section endommagée d'une extrémité d'aube endommagé de l'aube de rotor à réparer, en formant une surface de séparation mesurée après l'extraction de la section ou de chaque section endommagée ou de l'extrémité d'aube endommagée de l'aube de rotor, les données CAO étant adaptées au contour réel si un contour réel de la surface de séparation ainsi déterminée dévie de plus qu'une mesure définie par rapport à un contour de consigne de la surface de séparation déterminé par les données CAO de l'aube de rotor, un profilé de transition étant déterminé entre le contour réel et le contour de consigne ;
    c) mise en place successive de la section ou de chaque section extraite ou de l'extrémité d'aube entière sur la surface de séparation de l'aube de rotor à l'aide d'un procédé de fabrication rapide utilisant des données CAO tridimensionnelles de l'aube de rotor, le procédé de fabrication rapide étant exécuté de manière répétitive comme un procédé en deux étapes selon lequel, dans chaque première étape, un lit de poudre uniforme constitué d'une poudre métallique est prévu, lequel lit de poudre est formé à partir du même matériau de base en alliage que l'aube de rotor à réparer et, dans une seconde étape, la poudre métallique du lit de poudre étant soudée de manière sélective sur la base des données CAO tridimensionnelles adaptées.
  2. Procédé de réparation selon la revendication 1, caractérisé en ce que, dans chaque première étape, un lit de poudre uniforme d'une épaisseur maximale de 200 µm est prévu.
  3. Procédé de réparation selon la revendication 1 ou 2, caractérisé en ce que, dans chaque première étape, un lit de poudre d'une granulométrie comprise entre 10 et 150 µm est prévu.
  4. Procédé de réparation selon au moins l'une des revendications 1 à 3, caractérisé en ce que, dans une étape sur deux, la poudre métallique est soudée de manière sélective par soudage par faisceau laser.
  5. Procédé de réparation selon au moins l'une des revendications 1 à 4, caractérisé en ce que, dans une étape sur deux, la poudre métallique est soudée de manière sélective par soudage par faisceau d'électrons.
  6. Procédé de réparation selon au moins l'une des revendications 1 à 5, caractérisé en ce que la section ou chaque section séparée ou l'extrémité d'aube entière est surdimensionnée sur la surface de séparation de l'aube de rotor, l'extrémité d'aube réparée étant ensuite retravaillée.
EP07817519.7A 2006-09-21 2007-09-13 Procédé de réparation Not-in-force EP2064025B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006044555A DE102006044555A1 (de) 2006-09-21 2006-09-21 Reparaturverfahren
PCT/DE2007/001647 WO2008034413A1 (fr) 2006-09-21 2007-09-13 Procédé de réparation

Publications (2)

Publication Number Publication Date
EP2064025A1 EP2064025A1 (fr) 2009-06-03
EP2064025B1 true EP2064025B1 (fr) 2019-09-11

Family

ID=38896750

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07817519.7A Not-in-force EP2064025B1 (fr) 2006-09-21 2007-09-13 Procédé de réparation

Country Status (4)

Country Link
US (1) US20090271985A1 (fr)
EP (1) EP2064025B1 (fr)
DE (1) DE102006044555A1 (fr)
WO (1) WO2008034413A1 (fr)

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102006049219A1 (de) 2006-10-18 2008-04-30 Mtu Aero Engines Gmbh Hochdruckturbinen-Schaufel und Verfahren zur Reparatur von Hochdruckturbinen-Schaufeln
US20090026175A1 (en) * 2007-07-26 2009-01-29 Honeywell International, Inc. Ion fusion formation process for large scale three-dimensional fabrication
DE102008056336A1 (de) * 2008-11-07 2010-05-12 Mtu Aero Engines Gmbh Reparaturverfahren
US20100200189A1 (en) * 2009-02-12 2010-08-12 General Electric Company Method of fabricating turbine airfoils and tip structures therefor
EP2366476B1 (fr) * 2010-03-10 2014-07-02 General Electric Company Procédé de fabrication de surfaces portantes de turbine et structures à pointe associées
JP5618643B2 (ja) * 2010-06-14 2014-11-05 株式会社東芝 ガスタービン動翼の補修方法およびガスタービン動翼
US9175568B2 (en) 2010-06-22 2015-11-03 Honeywell International Inc. Methods for manufacturing turbine components
FR2962357B1 (fr) * 2010-07-09 2013-02-22 Snecma Procede de reparation ou de rechargement d'au moins une piece metallique
US20120156020A1 (en) * 2010-12-20 2012-06-21 General Electric Company Method of repairing a transition piece of a gas turbine engine
CH704448A1 (de) 2011-02-03 2012-08-15 Alstom Technology Ltd Verfahren zum Reparieren bzw. Rekonditionieren eines stark beschädigten Bauteils, insbesondere aus dem Heissgasbereich einer Gasturbine.
US9085980B2 (en) * 2011-03-04 2015-07-21 Honeywell International Inc. Methods for repairing turbine components
DE102011113357B4 (de) 2011-09-15 2024-08-29 Concept Laser Gmbh Verfahren zur Reparatur eines end- oder oberseitig verschlissenen Bauteils
US8506836B2 (en) 2011-09-16 2013-08-13 Honeywell International Inc. Methods for manufacturing components from articles formed by additive-manufacturing processes
US9266170B2 (en) 2012-01-27 2016-02-23 Honeywell International Inc. Multi-material turbine components
US9120151B2 (en) 2012-08-01 2015-09-01 Honeywell International Inc. Methods for manufacturing titanium aluminide components from articles formed by consolidation processes
US20150159585A1 (en) * 2013-12-06 2015-06-11 Caterpillar Inc. System and method for repair of cast component
GB201322647D0 (en) * 2013-12-20 2014-02-05 Renishaw Plc Additive manufacturing apparatus and method
DE102014222159A1 (de) 2014-10-30 2016-05-04 MTU Aero Engines AG Reparaturverfahren und Vorrichtung zum generativen Reparieren eines Bauteils
CN105499565B (zh) * 2015-12-02 2017-10-20 西安交通大学 用于野外环境受损金属零件快速修复的装置
EP3321189B1 (fr) * 2016-11-11 2021-03-03 Airbus Operations GmbH Procédé de reconditionnement d'une partie endommagée d'un composant et élément inséré
US11167454B2 (en) 2017-01-13 2021-11-09 General Electric Company Method and apparatus for continuously refreshing a recoater blade for additive manufacturing

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0289116A1 (fr) * 1987-03-04 1988-11-02 Westinghouse Electric Corporation Procédé et dispositif pour la coulée des matériaux pulvérisés
WO2006024844A2 (fr) * 2004-09-01 2006-03-09 Renishaw Plc Procede de commande d'une machine outil

Family Cites Families (35)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3568065D1 (en) * 1984-07-16 1989-03-09 Bbc Brown Boveri & Cie Process for the deposition of a corrosion-inhibiting layer, comprising protective oxide-forming elements at the base of a gas turbine blade, and a corrosion-inhibiting layer
US4743733A (en) * 1984-10-01 1988-05-10 General Electric Company Method and apparatus for repairing metal in an article
US5038014A (en) * 1989-02-08 1991-08-06 General Electric Company Fabrication of components by layered deposition
DE4327189C2 (de) * 1993-08-13 1996-02-01 Mtu Muenchen Gmbh Reparaturverfahren für im Kopf- oder Kantenbereich beschädigte Schaufelblätter von Turbomaschinen
EP0861927A1 (fr) * 1997-02-24 1998-09-02 Sulzer Innotec Ag Procédé de fabrication de structures monocristallines
US6355086B2 (en) * 1997-08-12 2002-03-12 Rolls-Royce Corporation Method and apparatus for making components by direct laser processing
US6326585B1 (en) 1998-07-14 2001-12-04 General Electric Company Apparatus for laser twist weld of compressor blisks airfoils
JP4434444B2 (ja) * 2000-07-14 2010-03-17 Ｊｓｒ株式会社 金属間化合物による被覆方法
EP1400339A1 (fr) 2002-09-17 2004-03-24 Siemens Aktiengesellschaft Procédé pour la fabrication d'un article tridimensionnel
JP3842717B2 (ja) * 2002-10-16 2006-11-08 株式会社日立製作所 溶接材料、溶接構造物、ガスタービン動翼及びガスタービン動翼又は静翼の補修方法
US7009137B2 (en) * 2003-03-27 2006-03-07 Honeywell International, Inc. Laser powder fusion repair of Z-notches with nickel based superalloy powder
DE10319494A1 (de) * 2003-04-30 2004-11-18 Mtu Aero Engines Gmbh Verfahren zur Reparatur und/oder Modifikation von Bauteilen einer Gasturbine
EP1645659B1 (fr) * 2003-06-11 2011-12-07 IHI Corporation Procede pour reparer une piece de machine, procede pour fa¢onner une piece de machine reparee, procede pour fabriquer une piece de machine, moteur de turbine a gaz, machine a decharge electrique, procede pour reparer un element de turbine et procede pour fa¢onner un element de turbine repare
DE10337866B4 (de) * 2003-08-18 2014-07-24 MTU Aero Engines AG Verfahren zur Herstellung von Bauteilen für Gasturbinen
RU2329276C2 (ru) * 2003-11-06 2008-07-20 Асахи Касеи Кемикалз Корпорейшн Стирольный сополимер и способ его получения
DE102004002551B4 (de) * 2004-01-17 2007-06-21 Mtu Aero Engines Gmbh Verfahren zur Reparatur von Bauteilen
DE102004042878A1 (de) * 2004-09-04 2006-03-09 Mtu Aero Engines Gmbh Verfahren zur Reparatur von Turbomaschinenschaufeln
US7339712B2 (en) * 2005-03-22 2008-03-04 3D Systems, Inc. Laser scanning and power control in a rapid prototyping system
US20060219329A1 (en) * 2005-03-29 2006-10-05 Honeywell International, Inc. Repair nickel-based superalloy and methods for refurbishment of gas turbine components
JP4546318B2 (ja) * 2005-04-15 2010-09-15 株式会社日立製作所 Ｎｉ基合金部材とその製造法及びタービンエンジン部品並びに溶接材料とその製造法
US20060231535A1 (en) * 2005-04-19 2006-10-19 Fuesting Timothy P Method of welding a gamma-prime precipitate strengthened material
US7807947B2 (en) * 2005-05-09 2010-10-05 3D Systems, Inc. Laser sintering process chamber gas curtain window cleansing in a laser sintering system
US20070111119A1 (en) * 2005-11-15 2007-05-17 Honeywell International, Inc. Method for repairing gas turbine engine compressor components
US8629368B2 (en) * 2006-01-30 2014-01-14 Dm3D Technology, Llc High-speed, ultra precision manufacturing station that combines direct metal deposition and EDM
US8477154B2 (en) * 2006-03-20 2013-07-02 Siemens Energy, Inc. Method and system for interactive virtual inspection of modeled objects
US8244025B2 (en) * 2006-03-20 2012-08-14 Siemens Energy, Inc. Method of coalescing information about inspected objects
US20080028605A1 (en) * 2006-07-28 2008-02-07 Lutz Andrew J Weld repair of metallic components
EP2047939A4 (fr) * 2006-08-02 2010-10-13 Toshiba Kk Procédé de prévention de l'érosion et élément avec section de prévention de l'érosion
WO2008094221A1 (fr) * 2006-09-26 2008-08-07 Pas Technologies Inc. Procédé de réparation d'un réseau de profilés aérodynamiques stationnaires dirigeant un écoulement tridimensionnel
US8140179B2 (en) * 2007-01-19 2012-03-20 S.E. Huffman Corp. Method and apparatus for repairing turbine components
US8691329B2 (en) * 2007-01-31 2014-04-08 General Electric Company Laser net shape manufacturing using an adaptive toolpath deposition method
US20080182017A1 (en) * 2007-01-31 2008-07-31 General Electric Company Laser net shape manufacturing and repair using a medial axis toolpath deposition method
US8324526B2 (en) * 2007-02-13 2012-12-04 Siemens Aktiengesellschaft Welded repair of defects lying on the inside of components
US20080288318A1 (en) * 2007-04-17 2008-11-20 Smart Tram Corp. Smart tram system and method for using
US20110180199A1 (en) * 2007-04-17 2011-07-28 United Technologies Corporation Powder -metallurgy braze preform and method of use

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0289116A1 (fr) * 1987-03-04 1988-11-02 Westinghouse Electric Corporation Procédé et dispositif pour la coulée des matériaux pulvérisés
WO2006024844A2 (fr) * 2004-09-01 2006-03-09 Renishaw Plc Procede de commande d'une machine outil

Also Published As

Publication number Publication date
EP2064025A1 (fr) 2009-06-03
DE102006044555A1 (de) 2008-04-03
WO2008034413A1 (fr) 2008-03-27
US20090271985A1 (en) 2009-11-05

Similar Documents

Publication Publication Date Title
EP2064025B1 (fr) Procédé de réparation
EP2081731B1 (fr) Procédé de réparation de pales de turbines à haute pression
DE4327189C2 (de) Reparaturverfahren für im Kopf- oder Kantenbereich beschädigte Schaufelblätter von Turbomaschinen
EP1620225B1 (fr) Procede de reparation et/ou modification de sous-groupes de turbine a gaz
EP1207004B1 (fr) Procédé de réparation d' aubes
EP2040876B1 (fr) Procédé de réparation d'aubes de turbine
DE602006000803T2 (de) Verfahren zum Reparieren einer Schaufel einer integral beschaufelten Turbinenrotorscheibe und Prüfkörper zur Durchführung des Verfahrens
WO2018145912A1 (fr) Procédé et dispositif pour la construction additive, à base d'un lit de poudre, d'un grand nombre de pièces de même nature
DE102009033835B4 (de) Verfahren zum Austauschen einer Schaufel eines Rotors mit integrierter Beschaufelung und ein derartiger Rotor
EP2038083A2 (fr) Procédé de réparation et/ou de remplacement d'éléments individuels d'une pièce d'une turbine à gaz
EP2352615A1 (fr) Procédé de fabrication ou de réparation de rotors de turbine à gaz à aubage intégral
DE102008058140A1 (de) Verfahren zur Reparatur von einkristallinen Turbinenschaufeln
WO2009143819A1 (fr) Procédé de réparation d'aubes monocristallines de turbine à haute pression par brasage par diffusion
DE10161824B4 (de) Verfahren zum Instandsetzen von verschlissenen oder außer Maß gefertigten Bauteilen
EP2229258B1 (fr) Procédé pour produire des rotors aubagés monoblocs
EP1838493A1 (fr) Procede de reparation d'aubes mobiles de turbine
DE102006005364A1 (de) Verfahren zum Reparieren eines Bauteils
WO2008138300A1 (fr) Procédé de réparation
DE102005021642A1 (de) Verfahren zur Herstellung eines einkristallinen Formkörpers
DE102008058141A1 (de) Verfahren zum Herstellen einer Schaufel für einen Rotor einer Strömungsmaschine
WO2010057475A1 (fr) Procédé de fabrication et/ou de réparation d'un rotor d'une turbomachine et rotor associé

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20090316

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK RS

17Q First examination report despatched

Effective date: 20111220

DAX Request for extension of the european patent (deleted)
RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: MTU AERO ENGINES GMBH

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: MTU AERO ENGINES AG

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20190408

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1177817

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190915

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502007016773

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20190911

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190911

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190911

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190911

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191211

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20191031

Year of fee payment: 13

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190911

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190911

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191212

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20191030

Year of fee payment: 13

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200113

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190911

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190911

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190911

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190911

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190911

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20191030

Year of fee payment: 13

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200224

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190911

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190911

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502007016773

Country of ref document: DE

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG2D Information on lapse in contracting state deleted

Ref country code: IS

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190911

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190913

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190930

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190930

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190913

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200112

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20190930

26N No opposition filed

Effective date: 20200615

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190911

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190930

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190911

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1177817

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190913

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190913

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502007016773

Country of ref document: DE

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20200913

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190911

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210401

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20070913

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200930

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190911

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200913

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190911